CN115450763A - Method and device for assembling high-pressure turbine air conduit - Google Patents

Method and device for assembling high-pressure turbine air conduit Download PDF

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Publication number
CN115450763A
CN115450763A CN202110637472.8A CN202110637472A CN115450763A CN 115450763 A CN115450763 A CN 115450763A CN 202110637472 A CN202110637472 A CN 202110637472A CN 115450763 A CN115450763 A CN 115450763A
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China
Prior art keywords
rear shaft
air conduit
turbine
grinding
air
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CN202110637472.8A
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Chinese (zh)
Inventor
田晓飞
王东
董龙腾
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AECC Commercial Aircraft Engine Co Ltd
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AECC Commercial Aircraft Engine Co Ltd
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Priority to CN202110637472.8A priority Critical patent/CN115450763A/en
Publication of CN115450763A publication Critical patent/CN115450763A/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P21/00—Machines for assembling a multiplicity of different parts to compose units, with or without preceding or subsequent working of such parts, e.g. with programme control
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B24—GRINDING; POLISHING
    • B24D—TOOLS FOR GRINDING, BUFFING OR SHARPENING
    • B24D15/00—Hand tools or other devices for non-rotary grinding, polishing, or stropping
    • B24D15/02—Hand tools or other devices for non-rotary grinding, polishing, or stropping rigid; with rigidly-supported operative surface
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
    • G01B21/00—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant
    • G01B21/22—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant for measuring angles or tapers; for testing the alignment of axes

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Grinding And Polishing Of Tertiary Curved Surfaces And Surfaces With Complex Shapes (AREA)

Abstract

The invention discloses a high-pressure turbine air conduit assembling method, which is used for an aeroengine, wherein the aeroengine comprises an air conduit, a turbine rear shaft and a positioning ring, and the method comprises the steps of S1, trial assembly of the air conduit, S2, measurement of an angle alpha, S3, calculation of the grinding thickness H and S4, and grinding of a shoulder neck of the air conduit; the invention also discloses a measuring tool and a grinding tool for the method. Through the assembling method of the high-pressure turbine air conduit, the thickness of the matching end face to be ground can be measured and calculated through one-time trial assembly, so that the assembly can be completed at one time in the next assembly, risks such as low working efficiency caused by repeated disassembly and assembly and possible component scratching and damage in the repeated assembly process are avoided, the assembly efficiency is improved, and the assembly quality is improved. Through the measuring tool, the measuring operation is convenient to carry out in the narrow space of the inner wall of the rear shaft of the turbine. Through the grinding tool, the air guide pipe is customized, and the grinding efficiency is improved.

Description

Method and device for assembling high-pressure turbine air guide pipe
Technical Field
The invention relates to the technical field of aero-engines, in particular to a method and a device for assembling a high-pressure turbine air conduit.
Background
When the engine is designed, cooling air needs to be supplied to the high-pressure turbine and the low-pressure turbine respectively, the high-pressure turbine is high in supply and demand pressure and temperature, and the low-pressure turbine is low in air supply pressure and temperature. In order to separate the two streams, an air duct is used between the high and low pressure rotors, by which the high pressure cooling gas is separated from the low pressure cooling gas. The air guide pipe is connected to the rear shaft of the high-pressure turbine, and the air guide pipe is difficult to install and fix due to the fact that a gap between the high-pressure turbine rotor and the low-pressure turbine rotor is small.
The novel air conduit connecting structure comprises an air conduit, a turbine rear shaft, a positioning ring and an elastic retainer ring, wherein an external thread is arranged at one end of the air conduit, an internal thread matched with the external thread is arranged at one end of the turbine rear shaft, the air conduit is in threaded connection with the turbine rear shaft, a shoulder neck is arranged at the tail end of the external thread of the air conduit, and a circle of boss is arranged on the rear end face of the air conduit; the inner ring of the turbine rear shaft is sequentially provided with a front end face, a first row of clamping grooves, a second row of clamping grooves and a rear end face along the assembling direction; the positioning ring comprises a plurality of inner ring grooves and a plurality of outer ring grooves, the inner ring grooves are matched with bosses of the air guide pipes, and the outer ring grooves are matched with a first row of clamping grooves and a second row of clamping grooves of the inner ring of the turbine rear shaft;
after the air conduit is screwed up with the turbine rear axle according to the tightening torque of regulation, its shoulder neck supports the preceding terminal surface of turbine rear axle, the locating ring aligns the back with air conduit circumference on the turbine rear axle through the round boss that the inner circle recess on the locating ring set up with air conduit rear end face, then packs in circlip between the second row of draw-in groove of locating ring and turbine rear axle inner circle, the benefit of this structure lies in solving air conduit and high-pressure turbine rear axle and has connected the problem of preventing changeing, can realize circumference location to air conduit. However, in the assembly process, it is often found that after the air conduit is screwed down by a torque, the boss at the end of the air conduit cannot be aligned with the inner ring groove of the positioning ring, so that the positioning ring and the spring retainer ring cannot be assembled. The air duct is disassembled in a commonly adopted solution mode, so that a bench worker uses a file grinding matching surface to enable a boss at the end part to rotate for a certain angle and then to be aligned with a groove of a positioning ring, the grinding amount is generally accumulated to be smaller than 0.1mm and needs to be ground for multiple times, the grinding amount at each time is difficult to control by manual grinding, the excessively large grinding amount and uneven grinding surface are easy to appear, the boss and the groove can be completely aligned after frequent grinding and trial assembly for multiple times, the air duct is disassembled and assembled at each time by needing auxiliary tools matched with the air duct, the workload is very high, the efficiency is low, the air duct is assembled for multiple times, and the risk of scratch, damage and the like of a component can be caused in the carrying process.
Disclosure of Invention
The invention aims to overcome the defects that the assembly efficiency of an air guide pipe and a positioning ring is low and the product is easy to damage in the prior art, and provides various high-pressure turbine air guide pipe assembly methods and devices.
The invention solves the technical problems through the following technical scheme:
a high-pressure turbine air conduit assembly method is used for an aeroengine, the aeroengine comprises an air conduit, a turbine rear shaft and a positioning ring, the air conduit is in threaded connection with the turbine rear shaft, and the positioning ring is arranged in an inner ring of the turbine rear shaft and is connected with the air conduit;
the high pressure turbine air duct assembly method includes the steps of:
s1, aligning an outer ring groove of the positioning ring with a second row of clamping grooves of the turbine rear shaft, and pushing the positioning ring into an inner ring of the turbine rear shaft along a direction opposite to an assembling direction; screwing the air guide pipe and the turbine rear shaft along the assembling direction until the shoulder neck of the air guide pipe is tightly attached to the front end face of the turbine rear shaft;
s2, measuring an angle alpha between a boss of the air conduit and an inner ring slot of the positioning ring;
s3, calculating the thickness H of the shoulder neck to be ground according to a formula, wherein the calculation formula of the thickness is as follows:
Figure BDA0003106359370000021
in the formula: p is the pitch of the air conduit;
s4, grinding the shoulder neck, wherein the grinding amount is the thickness H;
in the scheme, by the method for assembling the high-pressure turbine air conduit, the angular deviation between the boss of the air conduit and the inner ring groove of the positioning ring can be measured through one-time trial assembly, the angular deviation is analyzed in principle, the grinding amount required by the shoulder neck can be accurately calculated through a transformation formula, the successful assembly of the air conduit can be ensured after one-time grinding is finished, the waste of labor cost caused by repeated trial assembly and grinding in the past is effectively avoided, the assembly efficiency is improved, meanwhile, the risks of part scratching and damage caused by repeated disassembly and assembly and transportation are effectively reduced, the assembly efficiency is improved, and the assembly quality is improved.
Preferably, step S4 of the method for assembling a high-pressure turbine air duct is followed by the following steps:
s5, screwing the air guide pipe and the turbine rear shaft along the assembling direction again, and checking whether the inner ring groove of the positioning ring can be matched with the boss or not after reaching a specified screwing torque;
if yes, the steps S1 to S4 are not repeatedly executed, and the assembly is successful; if not, steps S2 to S4 are executed.
In the scheme, by adding the step S5, whether the one-time grinding meets the assembly requirement is checked, and the assembly success is ensured.
Preferably, the method for assembling the high-pressure turbine air duct further comprises the following steps between the steps S1 and S2:
s11, checking whether the positioning ring can be further pushed into the first row of clamping grooves of the turbine rear shaft and matched with the boss after the positioning ring is pushed into the second row of clamping grooves of the turbine rear shaft,
if yes, the steps S2-S4 are not executed any more, and the assembly is successful;
if not, steps S2 to S4 are executed.
In this embodiment, before the angle α is measured, the necessity of grinding can be determined in step S11.
Preferably, step S4 of the high pressure turbine air duct assembling method further includes:
and checking whether the surface of the air conduit has a high point, and if so, locally grinding the high point until the high point is not available.
In the scheme, the high points are checked and removed, so that the shoulder and neck obtain a smooth surface, and a better assembling effect is favorably obtained.
A measuring tool, for the above step S2, the measuring tool comprises a guide rail, a slider and a tightening rod, the guide rail comprises a track and a positioning block, the width of the positioning block is the same as the width of the inner ring slot of the positioning ring, the slider forms a fan-shaped angle β along the movement of the track, the number of bosses of the air duct is N, and the fan-shaped angle β is defined by:
Figure BDA0003106359370000041
the sliding block penetrates through the runway through a connecting piece to be connected with the tightening rod, and the connecting piece can freely slide in the runway.
In the scheme, the measuring tool is suitable for a measuring environment with a narrow inner ring of the rear shaft of the turbine, so that the measuring operation is simple and convenient; the slider can be tightly attached to the air conduit boss at any angle only by slightly shifting the slider by hands, and the measured angle deviation is accurate and high in precision.
Preferably, the thickness of the guide rail is not greater than the thickness of the positioning ring.
In the scheme, the thickness relation is set, so that the connecting piece between the sliding block and the tightening rod is not too long, the connecting piece can slide in the runway more flexibly, and the sliding operation is convenient.
Preferably, an outer diameter of the slider in the radial direction of the air guide pipe is not larger than an outer diameter of the boss of the air guide pipe in the radial direction of the air guide pipe.
In this scheme, through setting up the big or small relation of external diameter of this slider and boss for the slider can not produce because its external diameter is too big and interfere with the inner wall of turbine rear axle, leads to unable free slip between adjacent boss.
Preferably, a structural end face is formed on one side, facing the second row of clamping grooves, of the turbine rear shaft in an axial direction perpendicular to the turbine rear shaft, and the length of the tightening rod is greater than the distance from the structural end face to the rear end face of the turbine rear shaft.
In this scheme, the design of longer tightening rod can realize the location fastening of slider in open exterior space, has solved the problem that can't fix a position the slider at constrictive turbine rear axle inner chamber.
A grinding tool used in the above step S4, said grinding tool comprising a handle and a disk, said handle being connected to said disk,
the disk is coaxial with the shoulder neck of the air duct, and the inner diameter of the disk is equal to the outer diameter of the shoulder neck, and the end face of the disk is perpendicular to the axial direction of the disk.
In this scheme, this grinding tool is the specialized tool of the shoulder neck of grinding air conduit, only needs to be through pressing the rotation handle, can realize the disc bottom surface to the grinding work of air conduit shoulder neck, has improved grinding efficiency, avoids the damage of grinding in-process to air conduit again.
Preferably, the thickness of the disc is not less than the thickness of the shoulder neck of the air conduit.
In the scheme, the thickness relation is set, so that all parts of the surface of the shoulder neck, which need to be ground, can be ground in the same grinding, multiple times of grinding are avoided, and the grinding efficiency is improved.
The positive progress effects of the invention are as follows: by the method for assembling the high-pressure turbine air conduit, the thickness of the matching end face to be ground can be measured and calculated through one-time trial assembly, so that the assembly can be completed at one time in the next assembly, the risks of low working efficiency caused by repeated disassembly and assembly, and possible component scratching, damage and the like in the repeated assembly process are avoided, the assembly efficiency is improved, and the assembly quality is improved. By the measuring tool, the measuring operation is convenient to carry out in the narrow space of the inner wall of the rear shaft of the turbine. Through the grinding tool, the air guide pipe is customized, and the grinding efficiency is improved.
Drawings
FIG. 1 is a schematic assembly structure diagram of a high-pressure turbine air duct assembly method according to an embodiment of the invention.
Fig. 2 (a) is an exploded view (one) of an assembly structure of the method for assembling the high-pressure turbine air duct according to the embodiment of the invention.
Fig. 2 (b) is an exploded view (two) of an assembly structure of the method for assembling the high-pressure turbine air duct according to the embodiment of the present invention.
Fig. 2 (c) is an exploded view (iii) of the assembly structure of the high-pressure turbine air duct assembly method according to the embodiment of the present invention.
Fig. 2 (d) is an exploded view (iv) of the assembly structure of the method for assembling the high-pressure turbine air duct according to the embodiment of the present invention.
FIG. 3 is a schematic view of an angle α of a method of assembling a high pressure turbine air duct in accordance with an embodiment of the present invention.
Fig. 4 is a schematic structural diagram of a measurement tool according to an embodiment of the present invention.
Fig. 5 is a schematic structural diagram of a measurement tool according to an embodiment of the present invention.
Fig. 6 is a schematic diagram of a measurement method according to an embodiment of the invention.
FIG. 7 is a flow chart of steps of a method of assembling a high pressure turbine air duct in accordance with an embodiment of the present invention.
Fig. 8 is a schematic structural view of a grinding tool according to an embodiment of the present invention.
Description of reference numerals:
an air duct 1, a shoulder neck 5, a boss 6,
the turbine rear shaft 2, the front end surface 17, the first row of clamping grooves 9, the second row of clamping grooves 10, the structural end surface 18,
a positioning ring 3, an inner ring groove 7, an outer ring groove 8,
the spring retainer ring 4 is arranged on the upper portion of the spring retainer ring,
a guide rail 11, a slide block 12, a tightening rod 13, a positioning block 14, a runway 19, a connecting piece 20,
the length of the handle 15, the disc 16,
the assembly direction a.
Detailed Description
The invention is further illustrated by the following examples, which are not intended to limit the scope of the invention.
As shown in fig. 1, 2 (a) -2 (d), 3 and 7, the present invention provides a method for assembling a high-pressure turbine air conduit, which is used for an aircraft engine, where the aircraft engine includes an air conduit 1, a turbine rear shaft 2, and a positioning ring 3, the air conduit 1 is in threaded connection with the turbine rear shaft 2, the positioning ring 3 is disposed in an inner ring of the turbine rear shaft 2 and connected with the air conduit 1, and a circlip 4 is inserted between the positioning ring 3 and a second row of clamping grooves 10 of the inner ring of the turbine rear shaft 2;
the high-pressure turbine air duct assembling method comprises the following steps of:
s1, aligning an outer ring groove 8 of a positioning ring 3 with a second row of clamping grooves 10 of a turbine rear shaft 2, and pushing the positioning ring 3 into an inner ring of the turbine rear shaft 2 along a direction opposite to an assembling direction A; screwing the air conduit 1 and the turbine rear shaft 2 along the assembling direction A until the shoulder neck 5 of the air conduit 1 is tightly attached to the front end surface 17 of the turbine rear shaft 2;
s2, measuring an angle alpha between a boss 6 of the air conduit 1 and an inner ring slot of the positioning ring 3;
s3, calculating the thickness H of the shoulder neck 5 to be ground according to a formula, wherein the thickness calculation formula is as follows:
Figure BDA0003106359370000071
in the formula: p is the pitch of the air conduit 1;
s4, grinding the shoulder neck 5, wherein the grinding amount is the thickness H;
in the scheme, by the assembling method of the air conduit of the high-pressure turbine, the angle deviation between the boss 6 of the air conduit and the inner ring groove 7 of the positioning ring can be measured through one-time trial assembly, the analysis is carried out in principle, the grinding amount required by the shoulder neck 5 is accurately calculated through the angle deviation according to the transformation formula, the success of the assembly of the air conduit can be ensured after one-time grinding is finished, the waste of labor cost caused by repeated trial assembly and grinding in the past is effectively avoided, the assembling efficiency is improved, meanwhile, repeated disassembly and assembly are effectively reduced, the risk of part scratch and damage caused by carrying is effectively reduced, the assembling efficiency is improved, and the assembling quality is improved.
In the present embodiment, step S4 of the method for assembling a high-pressure turbine air duct further includes the following steps:
s5, screwing the air conduit 1 and the turbine rear shaft 2 along the assembling direction A again, and checking whether the inner ring groove 7 of the positioning ring 3 can be matched with the boss 6 or not after reaching the specified screwing torque;
if yes, the grinding amount required by one-time grinding is indicated, the air guide pipe, the positioning ring, the spring collar and the turbine rear shaft are assembled successfully, and the steps S1-S4 are not required to be executed repeatedly; if not, steps S2 to S4 are executed.
By adding this step S5, it is checked whether the one-time grinding meets the requirements of assembly, ensuring successful assembly.
In the present embodiment, the method for assembling the high pressure turbine air duct further includes the following steps between steps S1 and S2:
s11, checking whether the positioning ring 3 can be pushed into the first row of clamping grooves 9 of the turbine rear shaft 2 and matched with the boss 6 after the positioning ring 3 is pushed into the second row of clamping grooves 10 of the turbine rear shaft 2,
if so, indicating that no angle deviation exists between the boss of the air conduit and the outer ring groove of the positioning ring, and the air conduit, the positioning ring, the spring collar and the turbine rear shaft can be directly assembled successfully without executing the subsequent steps S2-S4; if not, steps S2 to S4 are executed.
Before the angle α is measured, the necessity of performing the grinding process can be judged by this step S11.
In the present embodiment, step S4 of the high pressure turbine air duct assembling method further includes:
the surface of the air duct 1 is checked for high points, and if there are high points, the high points are locally ground until there are no high points. The high points are checked and removed so that the neck 5 obtains a smooth surface, which is advantageous for obtaining a better fitting result.
As shown in fig. 4 to 6, a measuring tool, which may be used in the above step S2, includes a guide rail 11, a slider 12 and a tightening rod 13,
the guide rail 11 comprises a runway 19 and a positioning block 14, the width of the positioning block 14 is the same as that of the inner ring groove 7 of the positioning ring 3, the sliding block 12 forms a fan-shaped angle beta along the movement of the runway 19, the number of the bosses 6 is N, and the fan-shaped angle beta is as follows:
Figure BDA0003106359370000081
the sliding block 12 is connected with the tightening rod 13 through a connecting piece 20 passing through a track 19, and the connecting piece 20 can freely slide in the track 19, in this embodiment, the connecting piece 20 is a bolt, and the major diameter of the bolt is smaller than the width of the track 19 of the guide rail 11. However, in other embodiments, the connector 20 may be of other configurations that meet the requirements of the measuring tool.
The measuring tool is suitable for a measuring environment with a narrow inner ring of the turbine rear shaft 2, so that the measuring operation is simple and convenient; the slider 12 can be tightly attached to the boss 6 of the air conduit with any angle only by slightly shifting the slider 12 by hand, and the measured angle deviation is accurate and high in precision. Of course, in other embodiments, other tools meeting the measurement requirements may be used to measure the angle.
Wherein the thickness of the guide rail 11 is not more than that of the positioning ring 3; in the radial direction of the air guide tube 1, the outer diameter of the slider 12 is not larger than the outer diameter of the boss 6. The thickness relationship between the guide rail and the positioning ring is set, so that the bolt between the sliding block 12 and the tightening rod 13 is not too long, the bolt can slide in the runway 19 more flexibly, and the sliding operation is convenient. The outer diameter of the sliding block and the outer diameter of the boss are in size relation, so that the sliding block cannot interfere with the inner wall of the turbine rear shaft due to the fact that the outer diameter of the sliding block is too large, and the sliding block cannot freely slide between the adjacent bosses.
As shown in fig. 1, a structural end surface 18 is formed on a side of the first row of fastening grooves 9 facing the second row of fastening grooves 10 of the turbine rear shaft 2 in an axial direction perpendicular to the turbine rear shaft 2, and a length of the tightening rod 13 is greater than a distance from the structural end surface 18 to a rear end surface (not shown) of the turbine rear shaft 2. The design of longer tightening rod 13 can realize the location fastening of slider 12 in open exterior space, has solved the problem that can't fix a position slider 12 at narrow turbine rear axle 2 inner chamber.
Since the inner diameter of the turbine rear shaft 2 is usually very small, only one hand and a measuring tool can be accommodated, as shown in fig. 6, when measuring the angle α, the positioning block 14 of the guide rail 11 is clamped in the inner ring groove 7 of the positioning ring 3, the measuring tool is held by the palm of the left hand, the tightening rod 13 is moved by the right hand in the external open space, the right side of the slider 12 is tightly attached to the left side of the boss 6 of the air conduit 1 by the left hand, the tightening rod 13 is rotated to press and fix the position of the slider 12, and then the measuring tool is taken out of the cavity, and the angle α is measured.
As shown in fig. 8, a grinding tool, which can be used in the above step S4, includes a handle 15 and a disk 16, the handle 15 is connected to the disk 16, the handle 15 is a rotatable handle,
the disk 16 is coaxial with the shoulder neck 5 of the air duct 1, and the inner diameter of the disk 16 is equal to the outer diameter of the shoulder neck 5, and the end face of the disk 16 is perpendicular to the axial direction of the disk 16.
Because the bottom surface of the disc 16 may be designed to have a certain roughness, each grinding can achieve a trace grinding within 0.05 mm. When the grinding amount is required, the bottom of the disc 16 can be coated with a coloring agent, the shoulder neck 5 of the air duct 1 can be subjected to coloring inspection, and then the high points can be locally ground to be flat by a file, wherein the surface of the shoulder neck 5 can also be subjected to polishing treatment by a tool such as sand paper, so as to obtain a smoother surface, in other embodiments, the grinding amount of each time can be adjusted according to the roughness of the bottom surface of the disc, and the high points can be inspected in other aspects.
The grinding tool is a special tool for grinding the shoulder neck 5 of the air conduit 1, and can realize the grinding work of the disc bottom surface on the shoulder neck of the air conduit only by pressing the rotary handle, thereby improving the grinding efficiency and avoiding the damage to the air conduit 1 in the grinding process.
Wherein the thickness of the disc 16 is not less than the thickness of the shoulder neck 5 of the air duct 1. By setting the thickness relationship, all the parts of the surface of the shoulder neck 5 needing to be ground can be ground in the same grinding, multiple times of grinding are avoided, and the grinding efficiency is improved.
While specific embodiments of the invention have been described above, it will be appreciated by those skilled in the art that this is by way of example only, and that the scope of the invention is defined by the appended claims. Various changes and modifications to these embodiments may be made by those skilled in the art without departing from the spirit and scope of the invention, and these changes and modifications are within the scope of the invention.

Claims (10)

1. A high-pressure turbine air conduit assembly method is used for an aeroengine, the aeroengine comprises an air conduit, a turbine rear shaft and a positioning ring, the air conduit is in threaded connection with the turbine rear shaft, and the positioning ring is arranged in an inner ring of the turbine rear shaft and is connected with the air conduit;
the method for assembling the high-pressure turbine air duct is characterized by comprising the following steps of:
s1, aligning an outer ring groove of the positioning ring with a second row of clamping grooves of the turbine rear shaft, and pushing the positioning ring into an inner ring of the turbine rear shaft along a direction opposite to an assembling direction; screwing the air guide pipe and the turbine rear shaft along the assembling direction until the shoulder neck of the air guide pipe is tightly attached to the front end face of the turbine rear shaft;
s2, measuring an angle alpha between a boss of the air conduit and an inner ring groove of the positioning ring;
s3, calculating the thickness H of the shoulder neck to be ground according to a formula, wherein the calculation formula of the thickness is as follows:
Figure FDA0003106359360000011
in the formula: p is the pitch of the air conduit;
and S4, grinding the shoulder neck, wherein the grinding amount is the thickness H.
2. The high pressure turbine air duct assembly method of claim 1, further comprising, after step S4, the steps of:
s5, screwing the air guide pipe and the turbine rear shaft along the assembling direction again, and checking whether the inner ring groove of the positioning ring can be matched with the boss or not after reaching a specified screwing torque;
if not, steps S2 to S4 are executed again.
3. The high pressure turbine air duct assembly method of claim 1, further comprising, between steps S1 and S2, the steps of:
s11, checking whether the positioning ring can be further pushed into the first row of clamping grooves of the turbine rear shaft and matched with the boss after the positioning ring is pushed into the second row of clamping grooves of the turbine rear shaft,
if not, steps S2 to S4 are executed.
4. The high pressure turbine air duct assembly method of claim 1, step S4 of the high pressure turbine air duct assembly method further comprising:
and checking whether the surface of the air conduit has a high point, and if so, locally grinding the high point until the high point is not available.
5. A measuring tool for use in step S2 of the high pressure turbine air duct assembly method of claim 1, wherein the measuring tool comprises a guide rail, a slider, and a tightening rod,
the guide rail comprises a runway and a positioning block, the width of the positioning block is the same as that of an inner ring clamping groove of the positioning ring, the sliding block forms a sector angle beta along the movement of the runway, the number of bosses of the air conduit is N, and the sector angle beta is defined as follows:
Figure FDA0003106359360000021
the sliding block penetrates through the runway through a connecting piece to be connected with the tightening rod, and the connecting piece can freely slide in the runway.
6. The measurement tool of claim 5 wherein the thickness of the rail is no greater than the thickness of the locating ring.
7. The measuring tool of claim 5, wherein an outer diameter of the slider in a radial direction of the air guide pipe is not larger than an outer diameter of the boss of the air guide pipe in the radial direction of the air guide pipe.
8. The measuring tool of claim 5, wherein a side of the first row of slots of the turbine rear shaft facing the second row of slots forms a structural end surface in an axial direction perpendicular to the turbine rear shaft, and the length of the tightening rod is greater than a distance from the structural end surface to a rear end surface of the turbine rear shaft.
9. A grinding tool for use in step S4 of the high pressure turbine air duct assembling method according to claim 1, wherein said grinding tool includes a handle and a disk, said handle being connected to said disk,
the disk is coaxial with the shoulder neck of the air duct, and the inner diameter of the disk is equal to the outer diameter of the shoulder neck, and the end face of the disk is perpendicular to the axial direction of the disk.
10. The grinding tool of claim 9 wherein the thickness of the disk is not less than the thickness of the shoulder neck of the air conduit.
CN202110637472.8A 2021-06-08 2021-06-08 Method and device for assembling high-pressure turbine air conduit Pending CN115450763A (en)

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN117961481A (en) * 2024-03-29 2024-05-03 博世汽车转向系统（济南）有限公司 Press fitting tool and shaft seal press fitting method

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN117961481A (en) * 2024-03-29 2024-05-03 博世汽车转向系统（济南）有限公司 Press fitting tool and shaft seal press fitting method

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